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通过对类X-20高超声速飞行器的气动系数与高度、马赫数、攻角、侧滑角和舵偏角的关系进行分析,对各项气动系数进行了简化和拟合,并将舵偏增量视作控制输入,在此基础上建立了类X-20飞行器仿射非线性形式的控制模型,证明了它是可以输入输出精确线性化的,从而可以设计反馈线性化控制器.最后在存在大气密度、气动力矩系数和转动惯量不确定性情形下,针对原动力学模型进行闭环仿真研究,原动力学模型考虑地球旋转,气动数据直接从类X-20飞行器的气动数据表插值得到.仿真结果表明,所设计的控制律可以实现控制目标,具有较强鲁棒性.
By analyzing the relationship between the aerodynamic coefficient and the altitude, Mach number, angle of attack, side slip angle and steering angle of the X-20 hypersonic vehicle, the aerodynamic coefficients are simplified and fitted and the rudder is increased Which is regarded as control input. Based on this, a control model of affine nonlinear form of X-20 aircraft is established, which proves that it can input and output accurately and linearly, so that feedback linearization controller can be designed.Finally, Atmospheric dynamics, atmospheric density, moment of inertia moment and moment of inertia uncertainty, the closed-loop simulation of the dynamic model was performed. The dynamic model of the original model considered the rotation of the earth, and the aerodynamic data were directly interpolated from the aerodynamic data table of the X-20 class aircraft. , The designed control law can achieve the control goal and has strong robustness.